公开(公告)号：US11568099B2

公开(公告)日：2023-01-31

申请号：US17832898

申请日：2022-06-06

Applicant: Raytheon Technologies Corporation

Inventor： Peter Cocks ,  Wookyung Kim

IPC: G06F30/20 ,  G06F30/17 ,  G06N3/08 ,  G06F111/20

Abstract: A process for designing an internal turbine engine component including operating a test rig incorporating a physical morphing component having a first geometry and generating a data set of empirically determined component performance parameters corresponding to the first geometry. Providing the data set of empirically determined component performance parameters to a computational optimization system and automatically. Determining a geometry optimization of the morphing component. Altering the geometry of the morphing component to match the geometry optimization. Reiterating operating the test rig and providing the data set of empirically determined component performance parameters.

公开(公告)号：US20220333534A1

公开(公告)日：2022-10-20

申请号：US17231742

申请日：2021-04-15

Applicant: Raytheon Technologies Corporation

Inventor： Lance L. Smith ,  Timothy S. Snyder ,  Jeffrey M. Cohen ,  Peter Cocks ,  Sean C. Emerson

IPC: F02C9/40 ,  F02C7/22

Abstract: An assembly is provided for a turbine engine with a flowpath. This turbine engine assembly includes a fuel injection system. The fuel injection system includes a first fuel injector and a second fuel injector. The fuel injection system is configured to provide the first fuel injector with first fuel and provide the second fuel injector with second fuel. The first fuel may be or include ammonia. The second fuel is different than the first fuel. The second fuel may be or include hydrogen gas. The first fuel injector is configured to direct the first fuel into the flowpath for combustion. The second fuel injector is configured to direct the second fuel into the flowpath for combustion.

公开(公告)号：US20220299205A1

公开(公告)日：2022-09-22

申请号：US17665063

申请日：2022-02-04

Applicant: Raytheon Technologies Corporation

Inventor： Malcolm MacDonald ,  Sean C. Emerson ,  Brian M. Holley ,  Lance L. Smith ,  Peter Cocks

IPC: F23R3/40 ,  F02C7/224 ,  F02C6/00 ,  F02C3/30 ,  F02C3/20

Abstract: A turbo-expanding cracking assembly includes a plurality of stages each including a rotating blade coupled to an output shaft and a fixed stator, at least one heat exchanger configured to transfer heat to an ammonia containing fuel flow, and a catalyst that is configured to decompose an ammonia containing fuel flow into a flow containing hydrogen (H2).

公开(公告)号：US20220162999A1

公开(公告)日：2022-05-26

申请号：US16953566

申请日：2020-11-20

Applicant: Raytheon Technologies Corporation

Inventor： Peter Cocks ,  Lance L. Smith

IPC: F02C9/40 ,  C01B3/04 ,  C01B3/50 ,  F02C7/22 ,  F02C3/04

Abstract: A gas turbine engine includes a cracking device that is configured to decompose an ammonia flow into a flow that contains more hydrogen (H2) than ammonia (NH3), a first separation device that separates hydrogen downstream of the cracking device, wherein residual ammonia and nitrogen are exhausted as a residual flow. The separated flow contains more hydrogen than ammonia, and nitrogen is exhausted separately as a hydrogen flow. A combustor is configured to receive and combust the hydrogen flow from the separation device to generate a gas flow. A compressor section is configured to supply compressed air to the combustor. A turbine section is in flow communication with the gas flow produced by the combustor and is mechanically coupled to drive the compressor section.